Fuselage fitting



that? IVAN H. DRIGGS, 0F DAYTON, OHIO, ASSIGNOR T0 DAYTON-WRIGHTCOMPANY, OF

l DAYTON, 01H10, A CORPORATION OF DELAWARE.

FUSELAGE FITTING.

Application led. February 4, 1922. Serial No. 534,225.

To all whom it may concern.'

Be it known that I, IVAN H. Dulces, a citizen of the United States ofAmerica, residing at Dayton, county of Montgomery, and State of Ohio,have invented certain new and useful Improvements in Fuselage Fittings(Docket #49), of which the following is a full, clear, and exactdescription.

This invention relates to the construction of fuselage frames and isespecially adapted for use in fuselages having metallic longerons andstruts.

An object of this invention is to provide simple and effective means forsecurel attaching the metal stress members o the fuselage, such as thelongrons, struts and brace members without welding or brazing the stressmembers.

Further objects and advantages of the present invention will be apparent'from the following description, reference being had to theIaccompanying, drawing, wherein a preferred form of embodiment of thepresent invention is clearly shown.

In the drawing:

Fig. 1 is a top View showing the attachment of the longron andhorizontal strut, and wire pulls for the diagonal brace wires.

Fig. 2 is a view taken on line 2 2 of Fig. 1 showin the horizontal strutin section and showing all five Wire pulls for the ve brace wiresattached at the fitting.

Fig. 3 isa section on line 3--3 of Fig. 2.

Fig. 4c is a perspective view of the fitting.

In the drawing, similar reference characters refer to similar partsthroughout the several views.

Numeral 10 indicates a tubular metal longeron, 11 a vertical strut, and12 a horizontal strut, these struts being illustrated as also made ofmetallic tubes.

A metal strap 15, constructed of malleable metal so that it can be bentaround the longron, has its ends riveted together by rivets 16, asshown. One end of the strap 15 projects beyond the rivets and serves asa wire pull 17 for the diagonal brace wire 18 across the fuselage. Inorder to suitably attach the -abutting struts 11 and 12 to the strap 15there are provided the parts 20, preferably aluminum die castings whichmay be cast accurately enough so as not to require machining, which havea contour conforming to the surface of the strap 15 where they abut same(see Fig. 3). The castings 20 lit snugly in the open ends of struts 11and 12 and have shoulders 21 against which the struts abut. Thesecastings 20 may be attached to the strap 15 in various ways, but Iprefer to provide the bolts 22 and 23 which extend entirely through thelongron 10 and thus firmly hold the castings 20 and the strap 15 inplace. The bolts 22 and 23 of course must be set slightly off the centerline of strap 15 to permit their crossing within the longron, and thestrap 15 may be sli htly widened at the bolt heads as clearly ilustrated in the drawmg.

The malleable strap 15 is further provided with projecting lugs or earsalong its sides, these ears being bent out at an an le with the longron10 to form Wire pu s for the diagonal brace wires. The two ears 25 and26 extend at the sides and lie in the plane of the vertical strut 11 andare bent vertically downward to the angle at which the vert1cal diagonalwires come in. The two ears 27 and 28 extend at the sides and lie in theplane of the horizontal strut 12 and are bent horizontally to the angleat which the horizontal diagonal Wires come in. The strap fitting 15 maybe economically made by stamping from a plate of malleable metal andthen bending to the described shape.

This invention provides a fitting, very simple and cheap to manufacture,for use in metal fuselage construction wherein the stress members arenot Welded or brazed together but are pinned (the term pinned includingthe use of rivets, bolts, etc.) and hence heat treated stress membersmay be used and the higher strength of such metals taken advantage of.

While the form of mechanism herein shown and described, constitutes apreferred form of embodiment of the present invention, it is to beunderstood that other` forms might be adopted, all coming Within thescope of the claim which follows.

What I claim is as follows:

5 A composite metal ttng adapted for fuselage construction, including, ametal strap bent around a tubular longron and heving its ends'seeuredtogether to form a Wire pull, a small metal casting adapted to 10 besecured to the end of an abutting strut and to said strap, the surfaceof said casting News? abutting the strap being substantially arcuate,whereby the same com site fitting may be used for different angu ararrangements of said abuttn strut; and said wire 211. 1&5

En testimony Cuez'eoi I hereto a. my signature.

IVAN H. DRIGGS Witnesses:

Gmo. E. PASCO, WM. P. Pnsoo.

